CN114018527B - Semi-automatic interactive wind tunnel test scheme design method - Google Patents
Semi-automatic interactive wind tunnel test scheme design method Download PDFInfo
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- CN114018527B CN114018527B CN202111316805.3A CN202111316805A CN114018527B CN 114018527 B CN114018527 B CN 114018527B CN 202111316805 A CN202111316805 A CN 202111316805A CN 114018527 B CN114018527 B CN 114018527B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention discloses a semi-automatic interactive wind tunnel test scheme design method. The wind tunnel test scheme design method comprises the steps of establishing a database, a program library and a design test scheme, wherein the process of designing the test scheme comprises the steps of inputting information, determining a scaling factor, calculating load, screening a balance, selecting a device, virtually assembling, checking interference, simulating motion, configuring a camera and generating a report. The wind tunnel test scheme design method can integrate working experience into the primary test scheme design process, reduces the optimization iteration times of the primary test scheme design parameters, and shortens the primary test scheme design time; the preliminary test scheme can confirm the installation position of the aircraft model through computer virtual assembly, and the operation problem of the preliminary test scheme is found through the computer dynamic simulation test process, so that the preliminary test scheme is conveniently returned to be continuously modified, the final test scheme is obtained, and the problems encountered in the implementation process of the final test scheme are reduced.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a semi-automatic interactive wind tunnel test scheme design method.
Background
Wind tunnel tests are the main means for predicting the aerodynamic performance of an aircraft and acquiring key aerodynamic data required by the aircraft design. Aerodynamic problems in modern aerospace vehicle designs have been solved to date in large part by wind tunnel tests. The air tunnel test is used for carrying out direct physical simulation on the flow field of the aircraft, and the authenticity and reliability of the obtained test result cannot be replaced by other means. Therefore, wind tunnel tests play an important role in the development of aircraft. The advantages and disadvantages of the design of the wind tunnel test scheme are directly related to the effect and period of the whole wind tunnel test.
At present, the wind tunnel test scheme is designed mainly by the personal working experience of workers, the design time spent by different workers is greatly different, the design time is short for a few hours, and the design time is long for days, even weeks and months.
Currently, development of a semi-automatic interactive wind tunnel test scheme design method is needed.
Disclosure of Invention
The invention aims to provide a semi-automatic interactive wind tunnel test scheme design method.
The invention discloses a semi-automatic interactive wind tunnel test scheme design method, which comprises the following steps:
a. establishing a database and a program library
a1. Establishing a wind tunnel database, and inputting key parameters of a wind tunnel, wherein the key parameters comprise the size of a wind tunnel test section, the test Mach number, the Reynolds number, the temperature, the attack angle, the sideslip angle, the roll angle and the like;
a2. establishing a test device database, wherein the test device comprises a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a lock nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support; the test device database inputs the characteristic parameters, storage positions and working states of the existing test device;
a3. developing a parameterized design program of the test device by modules, inputting characteristic parameters into each module, and automatically generating a corresponding test device;
a4. developing a virtual assembly visualization program, and having assembly demonstration and motion demonstration functions;
a5. developing a motion simulation program, wherein the motion simulation program has a rigidity and strength checking function;
a6. developing an optical configuration program, and having the functions of optical camera installation and optical path demonstration;
b. design test protocol
b1. Inputting information; characteristic parameters of the aircraft are recorded, and the maximum projection area of the theoretical appearance of the aircraft is calculated;
b2. determining a scaling ratio; calculating the maximum projection area of the aircraft in the range of a test attack angle, a sideslip angle and a roll angle according to the requirement that the blocking degree epsilon of a conventional hypersonic wind tunnel is less than or equal to 8%, and determining the scaling of the aircraft model according to the preset model blocking degree epsilon as the ratio of the projection area of the aircraft model to the outlet area of the spray pipe to obtain the characteristic parameters of the aircraft model;
b3. calculating a load; according to the provided estimated aerodynamic coefficient of the aircraft, calculating the aerodynamic load of the aircraft model, namely the aerodynamic force and aerodynamic moment coefficient of the aircraft model relative to the reference point; taking an aircraft model press core from a reference point;
b4. a screening balance; selecting an existing balance in the test device database of the step a2 according to the pneumatic load of the aircraft model; if the existing balance does not meet the pneumatic load requirement of the aircraft model, designing a required balance by utilizing the balance module in the step a 3;
b5. a selection device; the method comprises the steps that a device comprising a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a lock nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support is selected in a test device database in the step a 2;
b6. virtually assembling; c, running the virtual assembly visualization program in the step a4, and assembling an aircraft model, a balance and a test device; calculating the distance between the aircraft model head and the nozzle outlet; calculating the position of the wind tunnel rotation center on the aircraft model;
b7. checking for interference; b, running the virtual assembly visualization program in the step a4, and dynamically performing visualization operation in the range of the test attack angle, the sideslip angle and the roll angle to check whether the aircraft model and the wind tunnel interfere, and if so, repeating the steps b 4-b 6 until the aircraft model and the wind tunnel do not interfere;
b8. motion simulation; b, running the motion simulation program in the step a5, and performing simulation check on the strength and the rigidity of the aircraft model, the balance and the test device to avoid the influence of insufficient strength and rigidity on the quality of wind tunnel test data of the aircraft model;
b9. configuring a camera; running the optical configuration program of the step a6, performing optical measurement device parameter setting including optical cameras and illumination, and performing optical measurement test dynamic simulation, and checking geometrical interferences among the optical cameras, the illumination, the aircraft model, the wind tunnel and the camera view fields by setting positions and angles of the optical cameras and the illumination, lens types and the aircraft model postures; through repeated iterative adjustment, geometric interference is avoided;
b10. generating a report; and determining relevant information of the wind tunnel test of the aircraft model, generating an information report, and completing the design of a wind tunnel test scheme.
The semi-automatic interactive wind tunnel test scheme design method can integrate working experience into the primary test scheme design process, reduces the optimization iteration times of the primary test scheme design parameters, and shortens the primary test scheme design time; the preliminary test scheme can confirm the installation position of the aircraft model through computer virtual assembly, and the operation problem of the preliminary test scheme is found through the computer dynamic simulation test process, so that the preliminary test scheme is conveniently returned to be continuously modified, the final test scheme is obtained, and the problems encountered in the implementation process of the final test scheme are reduced.
Drawings
FIG. 1 is a flow chart of a method of designing a semiautomatic interactive wind tunnel test scheme of the present invention;
FIG. 2 is an outline view of an aircraft model selected by the design method of the semi-automatic interactive wind tunnel test scheme of the invention;
FIG. 3 is a balance strut selected by the design method of the semiautomatic interactive wind tunnel test scheme of the invention;
FIG. 4 is a transition segment selected by the design method of the semiautomatic interactive wind tunnel test scheme of the invention;
FIG. 5 shows a copper sleeve selected by the design method of the semiautomatic interactive wind tunnel test scheme of the invention;
FIG. 6a is a schematic view of a positioning key (top view) selected by the design method of the semiautomatic interactive wind tunnel test scheme of the present invention;
FIG. 6b is a front view of a positioning key selected by the design method of the semiautomatic interactive wind tunnel test scheme of the present invention;
FIG. 7 is an assembly view of an aircraft model obtained by the semi-automatic interactive wind tunnel test solution design method of the present invention;
FIG. 8 is an assembled picture of an aircraft model in a wind tunnel;
FIG. 9 is a table of the final test plan design obtained by the semi-automatic interactive wind tunnel test plan design method of the present invention.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
Example 1
The aircraft model of the embodiment is HB-2, the hypersonic wind tunnel is CARDC phi 1 m hypersonic wind tunnel, and the implementation process is as follows:
the semi-automatic interactive wind tunnel test scheme design method of the embodiment comprises the following steps:
a. establishing a database and a program library
a1. Establishing a wind tunnel database, and inputting key parameters of a wind tunnel, wherein the key parameters comprise the size of a wind tunnel test section, the test Mach number, the Reynolds number, the temperature, the attack angle, the sideslip angle, the roll angle and the like;
a2. establishing a test device database, wherein the test device comprises a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a lock nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support; the test device database inputs the characteristic parameters, storage positions and working states of the existing test device;
a3. developing a parameterized design program of the test device by modules, inputting characteristic parameters into each module, and automatically generating a corresponding test device;
a4. developing a virtual assembly visualization program, and having assembly demonstration and motion demonstration functions;
a5. developing a motion simulation program, wherein the motion simulation program has a rigidity and strength checking function;
a6. developing an optical configuration program, and having the functions of optical camera installation and optical path demonstration;
b. design of test protocol as shown in FIG. 1
b1. Inputting information; characteristic parameters of the aircraft are recorded, and the maximum projection area of the theoretical appearance of the aircraft is calculated;
b2. determining a scaling ratio; calculating the maximum projection area of the aircraft in the range of a test attack angle, a sideslip angle and a roll angle according to the requirement that the blocking degree epsilon of a conventional hypersonic wind tunnel is less than or equal to 8%, determining the scaling of the aircraft model according to the preset model blocking degree epsilon as the ratio of the projection area of the aircraft model to the outlet area of the spray pipe, obtaining the characteristic parameters of the aircraft model, and obtaining the aircraft model shown in the screenshot of figure 2;
b3. calculating a load; according to the provided estimated aerodynamic coefficient of the aircraft, calculating the aerodynamic load of the aircraft model, namely the aerodynamic force and aerodynamic moment coefficient of the aircraft model relative to the reference point; taking an aircraft model press core from a reference point;
b4. a screening balance; selecting an existing balance in the test device database of the step a2 according to the pneumatic load of the aircraft model; if the existing balance does not meet the pneumatic load requirement of the aircraft model, designing a required balance by utilizing the balance module in the step a 3;
b5. a selection device; selecting devices in the test device database in the step a2, wherein the devices comprise a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a lock nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support, and specific devices are corresponding screenshots, namely, figures 3-5, 6a and 6b;
b6. virtually assembling; running the virtual assembly visualization program of step a4, and assembling an aircraft model, a balance and a test device, particularly a screenshot, namely fig. 7; calculating the distance between the aircraft model head and the nozzle outlet; calculating the position of the wind tunnel rotation center on the aircraft model, specifically, a screenshot, namely FIG. 8;
b7. checking for interference; b, running the virtual assembly visualization program in the step a4, and dynamically performing visualization operation in the range of the test attack angle, the sideslip angle and the roll angle to check whether the aircraft model and the wind tunnel interfere, and if so, repeating the steps b 4-b 6 until the aircraft model and the wind tunnel do not interfere;
b8. motion simulation; b, running the motion simulation program in the step a5, and performing simulation check on the strength and the rigidity of the aircraft model, the balance and the test device to avoid the influence of insufficient strength and rigidity on the quality of wind tunnel test data of the aircraft model;
b9. configuring a camera; running the optical configuration program of the step a6, performing optical measurement device parameter setting including optical cameras and illumination, and performing optical measurement test dynamic simulation, and checking geometrical interferences among the optical cameras, the illumination, the aircraft model, the wind tunnel and the camera view fields by setting positions and angles of the optical cameras and the illumination, lens types and the aircraft model postures; through repeated iterative adjustment, geometric interference is avoided;
b10. generating a report; and determining relevant information of the wind tunnel test of the aircraft model, generating an information report as shown in the screenshot of FIG. 9, and completing the design of a wind tunnel test scheme.
Although the embodiments of the present invention have been disclosed above, it is not limited to the use listed in the specification and the embodiments, but it can be fully applied to various fields suitable for the present invention. Further modifications and adaptations may readily be made by those skilled in the art without departing from the principles of the present invention, and thus the invention is not limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.
Claims (1)
1. The design method of the semiautomatic interactive wind tunnel test scheme is characterized by comprising the following steps of:
a. establishing a database and a program library
a1. Establishing a wind tunnel database, and inputting key parameters of a wind tunnel, wherein the key parameters comprise the size of a wind tunnel test section, the test Mach number, the Reynolds number, the temperature, the attack angle, the sideslip angle and the roll angle;
a2. establishing a test device database, wherein the test device comprises a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a lock nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support; the test device database inputs the characteristic parameters, storage positions and working states of the existing test device;
a3. developing a parameterized design program of the test device by modules, inputting characteristic parameters into each module, and automatically generating a corresponding test device;
a4. developing a virtual assembly visualization program, and having assembly demonstration and motion demonstration functions;
a5. developing a motion simulation program, wherein the motion simulation program has a rigidity and strength checking function;
a6. developing an optical configuration program, and having the functions of optical camera installation and optical path demonstration;
b. design test protocol
b1. Inputting information; characteristic parameters of the aircraft are recorded, and the maximum projection area of the theoretical appearance of the aircraft is calculated;
b2. determining a scaling ratio; calculating the maximum projection area of the aircraft in the range of a test attack angle, a sideslip angle and a roll angle according to the requirement that the blocking degree epsilon of a conventional hypersonic wind tunnel is less than or equal to 8%, and determining the scaling of the aircraft model according to the preset model blocking degree epsilon as the ratio of the projection area of the aircraft model to the outlet area of the spray pipe to obtain the characteristic parameters of the aircraft model;
b3. calculating a load; according to the provided estimated aerodynamic coefficient of the aircraft, calculating the aerodynamic load of the aircraft model, namely the aerodynamic force and aerodynamic moment coefficient of the aircraft model relative to the reference point; taking an aircraft model press core from a reference point;
b4. a screening balance; selecting an existing balance in the test device database of the step a2 according to the pneumatic load of the aircraft model; if the existing balance does not meet the pneumatic load requirement of the aircraft model, designing a required balance by utilizing the balance module in the step a 3;
b5. a selection device; the method comprises the steps that a device comprising a balance, a balance support rod, a back support, a copper sleeve, a balance front heat insulation sleeve, a balance rear heat insulation sleeve, a heat insulation gasket, a lock nut, a tensioning wedge key, a positioning key, a gasket, a switching section and a middle support is selected in a test device database in the step a 2;
b6. virtually assembling; c, running the virtual assembly visualization program in the step a4, and assembling an aircraft model, a balance and a test device; calculating the distance between the aircraft model head and the nozzle outlet; calculating the position of the wind tunnel rotation center on the aircraft model;
b7. checking for interference; b, running the virtual assembly visualization program in the step a4, and dynamically performing visualization operation in the range of the test attack angle, the sideslip angle and the roll angle to check whether the aircraft model and the wind tunnel interfere, and if so, repeating the steps b 4-b 6 until the aircraft model and the wind tunnel do not interfere;
b8. motion simulation; b, running the motion simulation program in the step a5, and performing simulation check on the strength and the rigidity of the aircraft model, the balance and the test device to avoid the influence of insufficient strength and rigidity on the quality of wind tunnel test data of the aircraft model;
b9. configuring a camera; running the optical configuration program of the step a6, performing optical measurement device parameter setting including optical cameras and illumination, and performing optical measurement test dynamic simulation, and checking geometrical interferences among the optical cameras, the illumination, the aircraft model, the wind tunnel and the camera view fields by setting positions and angles of the optical cameras and the illumination, lens types and the aircraft model postures; through repeated iterative adjustment, geometric interference is avoided;
b10. generating a report; and determining relevant information of the wind tunnel test of the aircraft model, generating an information report, and completing the design of a wind tunnel test scheme.
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